EP2281913B1 - Lubricated abradable coating - Google Patents
Lubricated abradable coating Download PDFInfo
- Publication number
- EP2281913B1 EP2281913B1 EP10251384.3A EP10251384A EP2281913B1 EP 2281913 B1 EP2281913 B1 EP 2281913B1 EP 10251384 A EP10251384 A EP 10251384A EP 2281913 B1 EP2281913 B1 EP 2281913B1
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- EP
- European Patent Office
- Prior art keywords
- coating layer
- coated article
- lubricant
- ceramic
- volume
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000000576 coating method Methods 0.000 title description 22
- 239000011248 coating agent Substances 0.000 title description 14
- 239000000314 lubricant Substances 0.000 claims description 34
- 239000011247 coating layer Substances 0.000 claims description 26
- 239000000919 ceramic Substances 0.000 claims description 25
- 239000000203 mixture Substances 0.000 claims description 13
- 239000000758 substrate Substances 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 9
- 239000004927 clay Substances 0.000 claims description 8
- 229910052751 metal Inorganic materials 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 239000010439 graphite Substances 0.000 claims description 5
- 229910002804 graphite Inorganic materials 0.000 claims description 5
- 239000002245 particle Substances 0.000 claims description 5
- 229910052582 BN Inorganic materials 0.000 claims description 4
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 4
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 claims description 4
- 238000005088 metallography Methods 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 3
- 229910002076 stabilized zirconia Inorganic materials 0.000 claims description 3
- 238000007751 thermal spraying Methods 0.000 claims 2
- 239000007921 spray Substances 0.000 description 10
- 238000005524 ceramic coating Methods 0.000 description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 5
- 230000003993 interaction Effects 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- 229920000642 polymer Polymers 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- VVQNEPGJFQJSBK-UHFFFAOYSA-N Methyl methacrylate Chemical compound COC(=O)C(C)=C VVQNEPGJFQJSBK-UHFFFAOYSA-N 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 239000000440 bentonite Substances 0.000 description 2
- 229910000278 bentonite Inorganic materials 0.000 description 2
- SVPXDRXYRYOSEX-UHFFFAOYSA-N bentoquatam Chemical compound O.O=[Si]=O.O=[Al]O[Al]=O SVPXDRXYRYOSEX-UHFFFAOYSA-N 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 229920000728 polyester Polymers 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000002002 slurry Substances 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 239000012720 thermal barrier coating Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000008199 coating composition Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 229910044991 metal oxide Inorganic materials 0.000 description 1
- 150000004706 metal oxides Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/347—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with layers adapted for cutting tools or wear applications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/224—Carbon, e.g. graphite
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/509—Self lubricating materials; Solid lubricants
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
- Y10T428/249987—With nonvoid component of specified composition
- Y10T428/24999—Inorganic
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/26—Web or sheet containing structurally defined element or component, the element or component having a specified physical dimension
- Y10T428/263—Coating layer not in excess of 5 mils thick or equivalent
- Y10T428/264—Up to 3 mils
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/31504—Composite [nonstructural laminate]
- Y10T428/31678—Of metal
Definitions
- the disclosure relates to turbine engine abradable coatings. More particularly, the disclosure relates to abradable coatings for interfacing with blade tips or vane airfoil tips.
- a wide variety of abradable coatings have been proposed for use in gas turbine engines. A particular location of concern is the interface between blade tips and adjacent non rotating structure (e.g., blade outer air seals (BOAS)).
- BOAS blade outer air seals
- a recent proposal was seen in US20090136740 (the '740 publication).
- the '740 publication discloses a coating layer comprising a metallic phase, a first ceramic phase and a second ceramic phase.
- the first ceramic phase may comprise at least one of boron nitride or graphite and the second ceramic phase may comprise at least one of clay or metal oxide.
- US2008/145649 A1 discloses a coating composition having a metallic matrix, a ceramic phase, and a lubricant phase.
- a coated article comprising a metallic substrate and a coating layer consisting of: 33% to 70% by volume ceramic, consisting of a stabilized zirconia, such as a yttria stabilized zirconia; and 5% to 50% by volume, when measured by optical metallography, of a lubricant selected from the group consisting of: hexagonal boron nitride (hBN); clay; graphite; and mixtures thereof, and a porosity, not including porosity within lubricant particles, of 5% to 30%, wherein the sum of the % by volume of the ceramic and the lubricant and the porosity is at least 95%; the coating layer not having a metal phase of greater than 5% by volume.
- a lubricant selected from the group consisting of: hexagonal boron nitride (hBN); clay; graphite; and mixtures thereof, and a porosity, not including porosity within lubricant particles, of 5% to 30%, wherein the sum of
- a machine comprising: a coated article as discussed above; and a component having a motion path relative to the article extending so that the coating layer forms a rub surface for the component.
- a method for forming a coated article including the steps of: providing an article comprising a metallic substrate; and codepositing the ceramic and the lubricant on the article to form the coated article.
- the article may be in a machine further having a moving component having a motion path extending so that the coating layer forms a rub surface.
- the coating/rub surface is on the moving component and/or a fixed component or a second moving component against which the moving component rubs.
- the coated article may be a blade outer air seal (BOAS) and moving component may be a blade.
- BOAS blade outer air seal
- coated article comprising metallic substrate and a coating layer.
- the coating layer includes a ceramic matrix and a lubricant within the matrix.
- the lubricant is selected from the group consisting of hBN, clay, graphite, and mixtures thereof.
- FIG. 1 shows a gas turbine engine 20 having a case assembly 22 containing concentric high and low pressure rotor shafts 24 and 25.
- the shafts are mounted within the case for rotation about an axis 500 which is normally coincident with central longitudinal axes of the case and shafts.
- the high speed pressure rotor shaft 24 is driven by the blades of a high speed/pressure turbine (HPT) section 26 to in turn drive the blades of a high speed/pressure compressor (HPC) 27.
- the low speed/pressure rotor shaft 25 is driven by the blades of a low speed/pressure turbine (LPT) section 28 to in turn drive the blades of a low speed/pressure compressor (LPC) section 29 and a fan 30.
- HPT high speed/pressure turbine
- LPC low speed/pressure compressor
- the turbine and/or compressor may have an intermediate speed/pressure section between the high and low sections.
- Air passes through the engine along a core flowpath 502 sequentially compressed by the low and high compressor sections 29 and 27, then passing through a combustor 32 wherein a portion of the air is combusted along with a fuel, and then passing through the high and low turbine sections 26 and 28 where work is extracted.
- Additional air is driven by the fan along a bypass flowpath 504.
- the bypass flowpath extends between an inner case 36 (sometimes identified as an intermediate case) and an outer case or duct 38.
- a leading portion of the exemplary duct 38 surrounds the fan 30.
- An inboard surface 40 of the duct 38 is closely spaced apart from fan blade tips 42.
- a circumferential array of fan exit guide vanes (FEGV) 50 may connect the inner case 36 to the duct 38.
- Various components exposed to gas along the core flowpath 502 have protective coatings (e.g., thermal barrier coatings (TBCs)). In certain locations, such coatings are subject to abrasion from relatively moving parts.
- TBCs thermal barrier coatings
- a first exemplary area is abrasion by compressor blade or turbine blade tips of the adjacent outboard boundary surface of the core flowpath.
- the exemplary outboard boundary surface 60 may be formed by one or more sequential circumferential arrays of blade outer air seals.
- FIG. 2 shows an exemplary BOAS-blade interaction
- FIG. 3 shows an exemplary cantilever vane-rotor interaction
- the individual segment 100 has an ID/inboard surface 102 forming a portion of the outboard boundary surface 60.
- a circular ring of such segments are positioned with the surfaces/faces 102 in close facing proximity to the tips 104 of the airfoils 106 of an adjacent blade stage 108.
- the airfoils 108 have respective leading and trailing edges 110 and 112 and pressure and suction sides.
- FIG. 3 shows the airfoil 120 of a cantilevered vane 122 having a leading edge 124, a trailing edge 126, and an inboard free tip or end 128.
- the inboard ends 128 of the stage of vanes are in close facing proximity to an adjacent portion of the outer surface 130 of a rotor 132.
- the surfaces 130 and 102 may have abradable coatings discussed below.
- FIG. 4 shows a metallic substrate 200 having a surface 202.
- the surface may be the ID-surface of the metallic substrate of the BOAS 100 or the OD-surface of the metallic substrate of the rotor 132.
- Atop the surface 202 is a bondcoat (bondcoat layer) 204.
- a lubricated ceramic coating 206 is atop the bondcoat 204.
- the exemplary substrate may be a nickel-based or cobalt-based superalloy or a titanium alloy.
- An exemplary bondcoat is an MCrAlY alloy (where M identifies one or more of Fe, Ni, and Co) or an aluminde.
- the exemplary ceramic may comprise a stabilized zirconia, such as yttria stabilized zirconia like 7YSZ.
- FIG. 5 shows the coating 206 as including ceramic (light areas) 220.
- the ceramic forms a matrix containing a solid lubricant (medium tone areas) 222 and separate porosity (dark areas) 224.
- the abradability of the ceramic combined with the lubrication of the lubricant may help minimize damage to the adjacent airfoil tips upon contact.
- Exemplary lubricant is selected from the group consisting of hexagonal boron nitride (hBN), clay, graphite, and mixtures thereof.
- the lubricant is 50% hBN (by volume and/or weight). Such is a mixture of mostly hBN with a smaller amount of clay (e.g., in a 90:10 ratio by weight).
- An exemplary bondcoat thickness is 0.005 inch (0.13mm), more broadly, 0.1-0.2mm or 0.5-3.0mm.
- Exemplary ceramic coating layer thickness is 0.015 inch (0.38mm), more broadly, 0.3-0.5mm or 0.2-0.8mm.
- the ceramic density is 33-70% (the remainder occupied by the lubricant and porosity), more narrowly 35-50%.
- Exemplary lubricant content is 5-50%, more narrowly 20-40% as measured by optical metallography (which treats porosity within the lubricant as if it was lubricant).
- the porosity (e.g., not including porosity within lubricant particles as just noted) is 5-30%, more narrowly 10-20%.
- compositions and porosities may be measured as a depth-wise average at a given location or average over an area. Such compositions may also be measured at any individual depth at such location or over such area (as in the case of a coating having a depth-wise gradient in composition or porosity).
- the ceramic coating layer may consist essentially of the ceramic, lubricant, and porosity (or porosity-formers prior to bake-off as is discussed further below).
- the content of such ceramic, lubricant, and porosity is at least 95% by volume. More particularly, essentially 100%. This, for example, is distinguished from metal-based coatings or coatings with substantial metal phases as are disclosed in US20090136740 . Thus, separate metal phases may account for an exemplary no more than 5% of the volume, more particularly essentially none.
- the exemplary airfoils may comprise metallic substrates either with or without coatings along the airfoil tips.
- One example is a nickel-based superalloy with an uncoated tip.
- the presence of the solid lubricant reduces the friction of the tip-to-seal (or rotor) rub and may reduce metal galling/transfer from the airfoil to the seal (or rotor). This can directly improve efficiency and life of both the airfoil and seal (or rotor).
- blow-by flow (of air or other gas) through the porosity may be reduced, thereby also improving efficiency. Heat generation and transfer to the seal substrate may similarly be reduced from the reduced friction and from the reduced porosity.
- the reduced heat transfer and reduced flow of air through the coating may reduce the formation of thermally grown oxides (TGO) atop the bond coat.
- An alternative exemplary airfoil is a titanium alloy having an abrasive tip coating (e.g., an aluminum oxide).
- the presence of the lubricant may have similar benefits to those described above including increasing life of the tip coating.
- Yet other embodiments might involve use of a similar lubricated coating on the tip in addition to the seal (or rotor). Particular benefits may be present where the coated surface is a rotor.
- Metal transferred from the airfoil has a lower tendency to adhere to the ceramic/solid lubricant coating contrasted with a coating having a substantial metallic phase. Centrifugal action may cause transferred metal to harmlessly shed (whereas a buildup could cause centrifugal loading to spall/delaminate the rotor coating). The reduction of buildup can also permit tighter design clearances.
- a variety of application techniques are possible. These include various thermal spray techniques, high velocity oxy-fuel (HVOF) techniques, and the like.
- Particular exemplary bond coat application techniques include air plasma spray, low pressure plasma spray (LPPS), vacuum plasma spray (VPS), and HVOF.
- Particular exemplary application techniques for the ceramic coating layer are air plasma spray and VPS.
- a more particular exemplary coating application combination is via air plasma spray, first of the bondcoat and then of the ceramic coating layer.
- Exemplary application of the ceramic coating layer may be via a blend of the ceramic, lubricant, and porosity-formers. In the exemplary lubricant blend of hBN and bentonite clay, the hBN and bentonite may initially be mixed and dispersed in water to form a slurry.
- the slurry may be spray dried to produce a mixture of particles.
- the mixture of particles (subject to appropriate size sorting) may provide improved flowability in spray equipment.
- Exemplary porosity-formers are polyester or methylmethacrylate or other polymer. As-deposited, the porosity-formers produce polymer phases within the ceramic coating layer. These polymer phases may be baked out to leave porosity (e.g., via a separate baking stage or upon use). Exemplary baking temperatures are at least 500°F (260°C) for methylmethacrylate and 900°F (482°C) for polyester.
- Alternative application techniques for the ceramic coating layer may be via separate introduction of the powders into the spray plume or codeposition of the powders with separate respective spray torches.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Materials Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Description
- The disclosure relates to turbine engine abradable coatings. More particularly, the disclosure relates to abradable coatings for interfacing with blade tips or vane airfoil tips.
- A wide variety of abradable coatings have been proposed for use in gas turbine engines. A particular location of concern is the interface between blade tips and adjacent non rotating structure (e.g., blade outer air seals (BOAS)). A recent proposal was seen in
US20090136740 (the '740 publication). The '740 publication discloses a coating layer comprising a metallic phase, a first ceramic phase and a second ceramic phase. The first ceramic phase may comprise at least one of boron nitride or graphite and the second ceramic phase may comprise at least one of clay or metal oxide.US2008/145649 A1 discloses a coating composition having a metallic matrix, a ceramic phase, and a lubricant phase. - According to a first aspect of the invention, there is provided a coated article comprising a metallic substrate and a coating layer consisting of: 33% to 70% by volume ceramic, consisting of a stabilized zirconia, such as a yttria stabilized zirconia; and 5% to 50% by volume, when measured by optical metallography, of a lubricant selected from the group consisting of: hexagonal boron nitride (hBN); clay; graphite; and mixtures thereof, and a porosity, not including porosity within lubricant particles, of 5% to 30%, wherein the sum of the % by volume of the ceramic and the lubricant and the porosity is at least 95%; the coating layer not having a metal phase of greater than 5% by volume.
- According to a second aspect of the invention, there is provided a machine comprising: a coated article as discussed above; and a component having a motion path relative to the article extending so that the coating layer forms a rub surface for the component.
- According to a third aspect of the invention, there is provided a method for forming a coated article as discussed above, including the steps of: providing an article comprising a metallic substrate; and codepositing the ceramic and the lubricant on the article to form the coated article.
-
-
FIG. 1 is a view of a gas turbine engine. -
FIG. 2 is an enlarged view of a blade seal interaction in the engine ofFIG. 1 . a yttria-stabilized-zirconia. The lubricant may comprise said hBN and said hBN may form 5-30% by volume of the coating layer. The lubricant may consist essentially of said hBN, clay, and mixtures thereof. The coating layer may consist essentially of said ceramic and said lubricant. - The article may be in a machine further having a moving component having a motion path extending so that the coating layer forms a rub surface. The coating/rub surface is on the moving component and/or a fixed component or a second moving component against which the moving component rubs. The coated article may be a blade outer air seal (BOAS) and moving component may be a blade.
- Another aspect of the disclosure involves a coated article according to claim 1 comprising metallic substrate and a coating layer. The coating layer includes a ceramic matrix and a lubricant within the matrix. The lubricant is selected from the group consisting of hBN, clay, graphite, and mixtures thereof.
- The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.
-
-
FIG. 1 is a view of a gas turbine engine. -
FIG. 2 is an enlarged view of a blade-seal interaction in the engine ofFIG. 1 . -
FIG. 3 is a schematic view of a cantilevered stator vane. -
FIG. 4 is a photomicrograph of a coating on a substrate. -
FIG. 5 is a photomicrograph of a lubricated ceramic layer in the coating ofFIG. 4 . - Like reference numbers and designations in the various drawings indicate like elements.
-
FIG. 1 shows agas turbine engine 20 having acase assembly 22 containing concentric high and lowpressure rotor shafts axis 500 which is normally coincident with central longitudinal axes of the case and shafts. The high speedpressure rotor shaft 24 is driven by the blades of a high speed/pressure turbine (HPT)section 26 to in turn drive the blades of a high speed/pressure compressor (HPC) 27. The low speed/pressure rotor shaft 25 is driven by the blades of a low speed/pressure turbine (LPT)section 28 to in turn drive the blades of a low speed/pressure compressor (LPC)section 29 and afan 30. In some engines the turbine and/or compressor may have an intermediate speed/pressure section between the high and low sections. Air passes through the engine along acore flowpath 502 sequentially compressed by the low andhigh compressor sections combustor 32 wherein a portion of the air is combusted along with a fuel, and then passing through the high andlow turbine sections bypass flowpath 504. The bypass flowpath extends between an inner case 36 (sometimes identified as an intermediate case) and an outer case orduct 38. A leading portion of theexemplary duct 38 surrounds thefan 30. Aninboard surface 40 of theduct 38 is closely spaced apart fromfan blade tips 42. To support and hold theduct 38, a circumferential array of fan exit guide vanes (FEGV) 50 may connect theinner case 36 to theduct 38. Various components exposed to gas along thecore flowpath 502 have protective coatings (e.g., thermal barrier coatings (TBCs)). In certain locations, such coatings are subject to abrasion from relatively moving parts. A first exemplary area is abrasion by compressor blade or turbine blade tips of the adjacent outboard boundary surface of the core flowpath. The exemplaryoutboard boundary surface 60 may be formed by one or more sequential circumferential arrays of blade outer air seals. A similar situation arises from abrasion of theinboard boundary surface 62 of the core flowpath by the inboard tips of so-called cantilevered vanes (the outboard ends of which may be formed with shroud segments of the outboard boundary surface 60). -
FIG. 2 shows an exemplary BOAS-blade interaction;FIG. 3 shows an exemplary cantilever vane-rotor interaction. InFIG. 2 , theindividual segment 100 has an ID/inboard surface 102 forming a portion of theoutboard boundary surface 60. A circular ring of such segments are positioned with the surfaces/faces 102 in close facing proximity to thetips 104 of theairfoils 106 of anadjacent blade stage 108. Theairfoils 108 have respective leading andtrailing edges - Similarly,
FIG. 3 shows theairfoil 120 of acantilevered vane 122 having a leadingedge 124, atrailing edge 126, and an inboard free tip orend 128. Theinboard ends 128 of the stage of vanes are in close facing proximity to an adjacent portion of theouter surface 130 of arotor 132. Thesurfaces -
FIG. 4 shows ametallic substrate 200 having asurface 202. The surface may be the ID-surface of the metallic substrate of theBOAS 100 or the OD-surface of the metallic substrate of therotor 132. Atop thesurface 202 is a bondcoat (bondcoat layer) 204. A lubricatedceramic coating 206 is atop thebondcoat 204. The exemplary substrate may be a nickel-based or cobalt-based superalloy or a titanium alloy. An exemplary bondcoat is an MCrAlY alloy (where M identifies one or more of Fe, Ni, and Co) or an aluminde. The exemplary ceramic may comprise a stabilized zirconia, such as yttria stabilized zirconia like 7YSZ. -
FIG. 5 shows thecoating 206 as including ceramic (light areas) 220. The ceramic forms a matrix containing a solid lubricant (medium tone areas) 222 and separate porosity (dark areas) 224. The abradability of the ceramic combined with the lubrication of the lubricant may help minimize damage to the adjacent airfoil tips upon contact. Exemplary lubricant is selected from the group consisting of hexagonal boron nitride (hBN), clay, graphite, and mixtures thereof. In more particular examples, the lubricant is 50% hBN (by volume and/or weight). Such is a mixture of mostly hBN with a smaller amount of clay (e.g., in a 90:10 ratio by weight). - An exemplary bondcoat thickness is 0.005 inch (0.13mm), more broadly, 0.1-0.2mm or 0.5-3.0mm. Exemplary ceramic coating layer thickness is 0.015 inch (0.38mm), more broadly, 0.3-0.5mm or 0.2-0.8mm. The ceramic density is 33-70% (the remainder occupied by the lubricant and porosity), more narrowly 35-50%. Exemplary lubricant content is 5-50%, more narrowly 20-40% as measured by optical metallography (which treats porosity within the lubricant as if it was lubricant). The porosity (e.g., not including porosity within lubricant particles as just noted) is 5-30%, more narrowly 10-20%. Such compositions and porosities may be measured as a depth-wise average at a given location or average over an area. Such compositions may also be measured at any individual depth at such location or over such area (as in the case of a coating having a depth-wise gradient in composition or porosity). Overall, the ceramic coating layer may consist essentially of the ceramic, lubricant, and porosity (or porosity-formers prior to bake-off as is discussed further below). The content of such ceramic, lubricant, and porosity is at least 95% by volume. More particularly, essentially 100%. This, for example, is distinguished from metal-based coatings or coatings with substantial metal phases as are disclosed in
US20090136740 . Thus, separate metal phases may account for an exemplary no more than 5% of the volume, more particularly essentially none. - The exemplary airfoils may comprise metallic substrates either with or without coatings along the airfoil tips. One example is a nickel-based superalloy with an uncoated tip. The presence of the solid lubricant reduces the friction of the tip-to-seal (or rotor) rub and may reduce metal galling/transfer from the airfoil to the seal (or rotor). This can directly improve efficiency and life of both the airfoil and seal (or rotor). To the extent that the presence of lubricant reduces porosity, blow-by flow (of air or other gas) through the porosity may be reduced, thereby also improving efficiency. Heat generation and transfer to the seal substrate may similarly be reduced from the reduced friction and from the reduced porosity. The reduced heat transfer and reduced flow of air through the coating may reduce the formation of thermally grown oxides (TGO) atop the bond coat. An alternative exemplary airfoil is a titanium alloy having an abrasive tip coating (e.g., an aluminum oxide). In such a system the presence of the lubricant may have similar benefits to those described above including increasing life of the tip coating. Yet other embodiments might involve use of a similar lubricated coating on the tip in addition to the seal (or rotor). Particular benefits may be present where the coated surface is a rotor. Metal transferred from the airfoil has a lower tendency to adhere to the ceramic/solid lubricant coating contrasted with a coating having a substantial metallic phase. Centrifugal action may cause transferred metal to harmlessly shed (whereas a buildup could cause centrifugal loading to spall/delaminate the rotor coating). The reduction of buildup can also permit tighter design clearances.
- A variety of application techniques are possible. These include various thermal spray techniques, high velocity oxy-fuel (HVOF) techniques, and the like. Particular exemplary bond coat application techniques include air plasma spray, low pressure plasma spray (LPPS), vacuum plasma spray (VPS), and HVOF. Particular exemplary application techniques for the ceramic coating layer are air plasma spray and VPS. A more particular exemplary coating application combination is via air plasma spray, first of the bondcoat and then of the ceramic coating layer. Exemplary application of the ceramic coating layer may be via a blend of the ceramic, lubricant, and porosity-formers. In the exemplary lubricant blend of hBN and bentonite clay, the hBN and bentonite may initially be mixed and dispersed in water to form a slurry. The slurry may be spray dried to produce a mixture of particles. The mixture of particles (subject to appropriate size sorting) may provide improved flowability in spray equipment. Exemplary porosity-formers are polyester or methylmethacrylate or other polymer. As-deposited, the porosity-formers produce polymer phases within the ceramic coating layer. These polymer phases may be baked out to leave porosity (e.g., via a separate baking stage or upon use). Exemplary baking temperatures are at least 500°F (260°C) for methylmethacrylate and 900°F (482°C) for polyester. Alternative application techniques for the ceramic coating layer may be via separate introduction of the powders into the spray plume or codeposition of the powders with separate respective spray torches.
- One or more embodiments have been described. Nevertheless, it will be understood that various modifications may be made. Accordingly, other embodiments are within the scope of the following claims.
Claims (9)
- A coated article comprising:a metallic substrate (200); anda coating layer (206) consisting of:33% to 70% by volume ceramic, consisting of a stabilized zirconia, such as a yttria stabilized zirconia; and5% to 50% by volume, when measured by optical metallography, of a lubricant selected from the group consisting of: hexagonal boron nitride (hBN); clay; graphite; and mixtures thereof, and a porosity, not including porosity within lubricant particles, of 5% to 30%, wherein the sum of the % by volume of the ceramic and the lubricant and the porosity is at least 95%;the coating layer not having a metal phase of greater than 5% by volume.
- The coated article of claim 1, wherein the coating layer (206) comprises:35 - 50% by volume said ceramic; and20 - 40% by volume said lubricant.
- The coated article of claim 1, wherein:the lubricant comprises hBN; andsaid hBN forms 5 - 30% by volume of the coating layer (206).
- The coated article of any preceding claim, further comprising:a bondcoat (204) between the substrate (200) and the coating layer (206);wherein, optionally,the bondcoat (204) has a thickness of 0.1 - 0.2 mm andthe coating layer (206) has a thickness 0.3 - 0.5 mm.
- The coated article of claim 1, wherein: said coating layer (206) has 10 - 20% by volume porosity
- The coated article of any preceding claim, wherein the coated article is:a blade outer air seal, the coating layer (206) being at least along an inner diameter (ID) face; ora rotor, the coating layer (206) being at least along an outer diameter (OD) surface.
- A machine comprising:the coated article (100; 132) of any preceding claim; anda component (106; 122) having a motion path relative to the article (100; 132) extending so that the coating layer (206) forms a rub surface for the component;wherein:the coated article is a blade outer air seal (100) and the component is a blade (106); orthe coated article is a rotor (132) and the component is a vane (122).
- A method for forming the coated article (100; 132) of any of claims 1 to 6, including the steps of:providing an article comprising a metallic substrate; andcodepositing the ceramic and the lubricant on the article to form the coated article.
- The method of claim 8, wherein the codepositing comprises:thermal spraying of said ceramic; andthermal spraying of said lubricant.
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US12/534,572 US20110027573A1 (en) | 2009-08-03 | 2009-08-03 | Lubricated Abradable Coating |
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EP2281913B1 true EP2281913B1 (en) | 2019-04-17 |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130071235A1 (en) * | 2011-09-20 | 2013-03-21 | Christopher W. Strock | Light weight abradable air seal |
US9598973B2 (en) | 2012-11-28 | 2017-03-21 | General Electric Company | Seal systems for use in turbomachines and methods of fabricating the same |
US9316110B2 (en) | 2013-08-08 | 2016-04-19 | Solar Turbines Incorporated | High porosity abradable coating |
US11097511B2 (en) | 2014-11-18 | 2021-08-24 | Baker Hughes, A Ge Company, Llc | Methods of forming polymer coatings on metallic substrates |
US10300627B2 (en) | 2014-11-25 | 2019-05-28 | Baker Hughes, A Ge Company, Llc | Method of forming a flexible carbon composite self-lubricating seal |
US10533439B2 (en) * | 2014-12-16 | 2020-01-14 | United Technologies Corporation | Gas turbine engine component with abrasive surface formed by electrical discharge machining |
US9896756B2 (en) | 2015-06-02 | 2018-02-20 | United Technologies Corporation | Abradable seal and method of producing a seal |
US10125274B2 (en) * | 2016-05-03 | 2018-11-13 | Baker Hughes, A Ge Company, Llc | Coatings containing carbon composite fillers and methods of manufacture |
US11209010B2 (en) * | 2017-02-13 | 2021-12-28 | Raytheon Technologies Corporation | Multilayer abradable coating |
US11597991B2 (en) * | 2017-06-26 | 2023-03-07 | Raytheon Technologies Corporation | Alumina seal coating with interlayer |
US20190186281A1 (en) * | 2017-12-20 | 2019-06-20 | United Technologies Corporation | Compressor abradable seal with improved solid lubricant retention |
CN111334740A (en) * | 2018-12-19 | 2020-06-26 | 辽宁省轻工科学研究院有限公司 | High-temperature wear-resistant self-lubricating coating and preparation method thereof |
US11149854B2 (en) * | 2019-02-07 | 2021-10-19 | Raytheon Technologies Corporation | High pressure compressor seal-ring with improved wear resistance |
CN111850451A (en) * | 2019-04-30 | 2020-10-30 | 上海大学 | Self-lubricating wear-resistant composite coating and preparation method thereof |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5185217A (en) * | 1989-09-08 | 1993-02-09 | Toyota Jidosha Kabushiki Kaisha | Relatively displacing apparatus |
US5536022A (en) * | 1990-08-24 | 1996-07-16 | United Technologies Corporation | Plasma sprayed abradable seals for gas turbine engines |
US5603603A (en) * | 1993-12-08 | 1997-02-18 | United Technologies Corporation | Abrasive blade tip |
US8114821B2 (en) * | 2003-12-05 | 2012-02-14 | Zulzer Metco (Canada) Inc. | Method for producing composite material for coating applications |
CA2585992C (en) * | 2006-06-08 | 2014-06-17 | Sulzer Metco (Us) Inc. | Dysprosia stabilized zirconia abradable |
US7448843B2 (en) * | 2006-07-05 | 2008-11-11 | United Technologies Corporation | Rotor for jet turbine engine having both insulation and abrasive material coatings |
US7686570B2 (en) * | 2006-08-01 | 2010-03-30 | Siemens Energy, Inc. | Abradable coating system |
US7726937B2 (en) * | 2006-09-12 | 2010-06-01 | United Technologies Corporation | Turbine engine compressor vanes |
US20080131686A1 (en) * | 2006-12-05 | 2008-06-05 | United Technologies Corporation | Environmentally friendly wear resistant carbide coating |
US20080145649A1 (en) * | 2006-12-14 | 2008-06-19 | General Electric | Protective coatings which provide wear resistance and low friction characteristics, and related articles and methods |
US8303247B2 (en) * | 2007-09-06 | 2012-11-06 | United Technologies Corporation | Blade outer air seal |
US7998604B2 (en) * | 2007-11-28 | 2011-08-16 | United Technologies Corporation | Article having composite layer |
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